公开(公告)号：US06382565B1

公开(公告)日：2002-05-07

申请号：US08816728

申请日：1997-03-13

申请人： Richard A. Fowell

发明人： Richard A. Fowell

IPC分类号： B64G128

CPC分类号： B64G1/24 ,  B64G1/281 ,  B64G1/283 ,  B64G1/285 ,  B64G1/286 ,  B64G1/288 ,  B64G1/36 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365 ,  B64G1/38 ,  G05D1/0883

摘要： Methods and systems for stabilizing satellite spin about an intermediate inertia axis (Z) are disclosed. A set of gyros (22) sense the X component and the Y component of the angular velocity of the satellite body. A single degree of freedom momentum wheel (26) has a fixed transverse orientation with respect to the intermediate axis in order to store momentum. In one embodiment, the momentum wheel (26) is oriented to store momentum parallel to the Y axis. A tachometer (30) senses the rotation rate of the momentum wheel (26). A processor (24) forms a control signal representative of a control torque to be applied to the momentum wheel (26). The control torque is based upon the X component and the Y component of angular velocity of the satellite, and the angular velocity of the momentum wheel (26). These methods and systems may also be used to invert the spin direction of spinning satellites, ensure tumble recover to a preferred orientation, and stabilize the body spin axis against nutation, dynamic imbalance and external torques.

摘要翻译： 公开了围绕中间惯性轴（Z）稳定卫星旋转的方法和系统。 一组陀螺仪（22）感测卫星体的角速度的X分量和Y分量。 单个自由度动量轮（26）相对于中间轴线具有固定的横向取向以便储存动量。 在一个实施例中，动量轮（26）被定向成存储平行于Y轴的动量。 转速计（30）感测动量轮（26）的旋转速度。 处理器（24）形成表示要施加到动量轮（26）的控制扭矩的控制信号。 控制扭矩基于卫星的角速度的X分量和Y分量以及动量轮（26）的角速度。 这些方法和系统也可以用于反转旋转卫星的旋转方向，确保滚筒恢复到优选的方向，并且使身体旋转轴线抵抗章动，动态不平衡和外部扭矩。

公开(公告)号：US06305646B1

公开(公告)日：2001-10-23

申请号：US09468701

申请日：1999-12-21

申请人： Jeoffrey R. McAllister ,  Richard A. Fowell

发明人： Jeoffrey R. McAllister ,  Richard A. Fowell

IPC分类号： B64G100

CPC分类号： B64G1/242 ,  B64G1/26 ,  G01C21/24 ,  G05D1/0883

摘要： A method, apparatus, article of manufacture, and a memory structure for controlling the eccentricity of an orbit. One embodiment of the present invention is described by a method comprising the step of performing a program of eccentricity control maneuvers wherein the control maneuvers are executed at times and in directions selected to apply substantially all eccentricity control along a line of antinodes. In one embodiment, the control maneuvers arc tangential maneuvers, and each control maneuver is applied near the line of antinodes. Provision is made for performing additional maneuvers, including node retargcting maneuvers during specified intervals. Another embodiment of the invention is described by a satellite in a substantially geosynchronous orbit having a satellite control system with a processor implementing instructions to perform control maneuvers as described above. Yet another embodiment of the present invention is described by a command facility comprising a processor for implementing instructions to perform the program control maneuvers described above, and a communicatively coupled transmitter for transmitting the commands to the satellite.

摘要翻译： 一种用于控制轨道的偏心度的方法，装置，制品和存储结构。 本发明的一个实施例通过一种方法来描述，该方法包括以下步骤：执行偏心控制机动程序，其中控制操作在选择的时间和方向上被执行，以沿着一条波腹线应用基本上所有的偏心控制。 在一个实施例中，控制操作是切向机动，并且每个控制机动被施加在波腹线附近。 经费用于执行附加操作，包括在指定时间间隔内的节点返回操作。 本发明的另一实施例由具有卫星控制系统的基本地球同步轨道的卫星来描述，所述卫星控制系统具有执行如上所述执行控制机动的指令的处理器。 本发明的另一个实施例由包括用于执行上述程序控制操作的指令的处理器以及用于将命令发送到卫星的通信耦合发射机的命令设备来描述。

公开(公告)号：US4883244A

公开(公告)日：1989-11-28

申请号：US137225

申请日：1987-12-23

申请人： A. Dorian Challoner ,  U. A. von der Embse ,  Mark P. Mitchell ,  Donald C. D. Chang ,  Richard A. Fowell ,  Ken Y. Huang ,  Joseph H. Hayden ,  Gene E. Allen

发明人： A. Dorian Challoner ,  U. A. von der Embse ,  Mark P. Mitchell ,  Donald C. D. Chang ,  Richard A. Fowell ,  Ken Y. Huang ,  Joseph H. Hayden ,  Gene E. Allen

IPC分类号： B64G1/36 ,  B64G1/24 ,  B64G1/28 ,  B64G1/32 ,  G05D1/08

CPC分类号： G05D1/0883 ,  B64G1/24 ,  B64G1/28 ,  B64G1/32 ,  B64G1/281

摘要： Agile (electronically steerable) beam sensing with associated on-board processing, previously used exclusively for positioning of antennas for beam formation and tracking in communications systems, is now also used for satellite active attitude determination and control. A spinning satellite (100) is nadir oriented and precessed at orbit rate using magnetic torquing determined through use of an on-board stored magnetic field model (520) and attitude and orbit estimates (212). A Kalman filter (211) predicts parameters (202, 203) associated with a received signal (204) impinging on the satellite's wide angle beam antenna (201). The antenna system measures the error between the parameter predictions and observed values and sends appropriate error signals (207) to the Kalman filter for updating its estimation procedures. The Kalman filter additionally outputs the spacecraft attitude error signals (215) to an attitude control law (213), which determines commands to attitude-altering magnetic torque elements (220) to close the control loop via the spacecraft dynamics (230).

公开(公告)号：US20080199077A1

公开(公告)日：2008-08-21

申请号：US11707674

申请日：2007-02-16

申请人： Richard A. Fowell

发明人： Richard A. Fowell

IPC分类号： G06K9/46 ,  B64G1/00 ,  G06K9/36

CPC分类号： B64G1/361 ,  B64G1/1007 ,  G06K9/00087 ,  G06K9/00617 ,  G06K9/6211

摘要： In an exemplary embodiment, a pattern is recognized from digitized images. A first image metric is computed from a first digitized image and a second image metric is computed from a second digitized image. A composite image metric is computed as a function of the first image metric and the second image metric, and a pattern is identified by comparing the composite image metric against a reference image metric. The function may be a simple average or a weighted average. The image metric may include a separation distance between features, or a measured area of a feature, or a central angle between two arcs joining a feature to two other features, or an area of a polygon whose vertices are defined by features, or a second moment of a polygon whose vertices are defined by features. The images may include without limitation images of friction ridges, irises, or stars.

摘要翻译： 在示例性实施例中，从数字化图像识别图案。 从第一数字化图像计算第一图像度量，并且从第二数字化图像计算第二图像度量。 作为第一图像度量和第二图像度量的函数计算合成图像度量，并且通过将合成图像度量与参考图像度量进行比较来识别图案。 该函数可以是简单的平均值或加权平均值。 图像度量可以包括特征之间的间隔距离，或特征的测量区域，或将特征连接到两个其他特征的两个弧之间的中心角，或其顶点由特征定义的多边形的区域，或第二 顶点由特征定义的多边形的时刻。 图像可以包括但不限于摩擦脊，虹膜或星星的图像。

公开(公告)号：US07025307B2

公开(公告)日：2006-04-11

申请号：US10318715

申请日：2002-12-13

申请人： Hanching Grant Wang ,  Richard A. Fowell ,  Che-Hang C. Ih

发明人： Hanching Grant Wang ,  Richard A. Fowell ,  Che-Hang C. Ih

IPC分类号： E03H5/00

CPC分类号： B64G1/407 ,  B64G1/222 ,  B64G1/242 ,  B64G1/26 ,  B64G1/283 ,  B64G1/285 ,  B64G1/32 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365 ,  B64G1/443 ,  B64G1/66

摘要： A method and an apparatus for controlling the attitude and momentum of a spacecraft while deploying an appendage from the spacecraft. The method uses solar tacking and similar techniques to produce differential solar torques that are used to control the momentum and attitude of the spacecraft during the appendage deployment.

摘要翻译： 一种用于在从航天器部署附件的同时控制航天器的姿态和动量的方法和装置。 该方法使用太阳能固定和类似技术来产生差分太阳能转矩，用于控制附件部署期间航天器的动量和姿态。

公开(公告)号：US06439511B1

公开(公告)日：2002-08-27

申请号：US09625690

申请日：2000-07-26

申请人： James H. Ingersoll, Jr. ,  Richard A. Fowell

发明人： James H. Ingersoll, Jr. ,  Richard A. Fowell

IPC分类号： B64G144

CPC分类号： B64G1/44

摘要： A solar wing control system for avoiding thermal shock to a solar wing includes an eclipse exit slew profile generator having an eclipse exit slew rate output for rotating the solar wing from an eclipse exit angle to a solar power generation angle to control solar wing heating rate.

摘要翻译： 一种用于避免对太阳能翼的热冲击的太阳能翼控制系统包括具有日蚀出口压摆率输出的日食出口摆轮廓发生器，用于将太阳翼从日食出射角旋转到太阳能发电角以控制太阳能翼加热速率。

公开(公告)号：US6135389A

公开(公告)日：2000-10-24

申请号：US39883

申请日：1998-03-16

申请人： Richard A. Fowell

发明人： Richard A. Fowell

IPC分类号： B64G1/10 ,  B64G1/24 ,  B64G1/36 ,  B64G1/66 ,  B64G1/00

CPC分类号： B64G1/66 ,  B64G1/24 ,  B64G1/242 ,  B64G1/1007 ,  B64G1/1021 ,  B64G1/365

摘要： A method for steering the payload beam of a satellite in a non-geostationary orbit toward an intended service area having known geographical dimensions in order to obtain improved pointing performance with a corresponding reduction in the demand on onboard hardware and software systems. The method comprises the steps of determining a subterranean target point and a direction fixed in the payload beam, calculating the orientation that points the payload beam direction through the subterranean target point, and maintaining this payload beam orientation using an on-board attitude control system.

摘要翻译： 用于将非对地静止轨道中的卫星的有效载荷波束朝向具有已知地理尺寸的预期服务区域进行操纵的方法，以便获得改进的指向性能，同时降低对车载硬件和软件系统的需求。 该方法包括以下步骤：确定地下目标点和固定在有效载荷波束中的方向，计算通过地下目标点指示有效载荷波束方向的方位，以及使用车载姿态控制系统保持该有效载荷束取向。

公开(公告)号：US6032903A

公开(公告)日：2000-03-07

申请号：US22991

申请日：1998-02-12

申请人： Richard A. Fowell ,  Qinghong W. Wang

发明人： Richard A. Fowell ,  Qinghong W. Wang

IPC分类号： B64G1/24 ,  B64G1/26 ,  B64G1/28

CPC分类号： B64G1/28 ,  B64G1/24 ,  B64G1/26 ,  B64G1/281 ,  B64G1/283 ,  B64G1/285 ,  B64G1/288 ,  B64G2001/245

摘要： Structures and methods are provided to effect satellite maneuvers in the presence of disturbance torques with enhanced fuel efficiency. A thruster control loop is combined with a wheel control loop in which the wheels respond to an estimate of the disturbance torques (e.g., an angular acceleration estimate, a thruster torque command or a filtered thruster torque command) to create a counteracting gyroscopic torque. Simulations of the invention's methods have shown they have the authority of all-thruster control systems and fuel efficiency that rivals that that of all-wheel control systems.

摘要翻译： 提供了结构和方法，以在存在具有提高的燃料效率的干扰转矩的情况下实现卫星操纵。 推进器控制回路与车轮控制回路相结合，其中车轮对干扰转矩（例如，角加速度估计，推进器转矩指令或滤波推进器转矩指令）的估计作出响应，以产生抵消的陀螺转矩。 本发明方法的仿真表明，它们具有全推进器控制系统和燃油效率的权威，与全轮控制系统相当。

公开(公告)号：US5758846A

公开(公告)日：1998-06-02

申请号：US816727

申请日：1997-03-13

申请人： Richard A. Fowell

发明人： Richard A. Fowell

IPC分类号： B64G1/24 ,  B64G1/28 ,  B64G1/36 ,  B64G1/38 ,  G05D1/08

CPC分类号： B64G1/24 ,  B64G1/281 ,  B64G1/285 ,  B64G1/288 ,  B64G1/36 ,  B64G1/38 ,  G05D1/0883 ,  B64G1/283 ,  B64G1/286 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365

摘要： A method and system are disclosed for inverting a satellite spinning about a first desired spin axis to spin about a second desired spin axis substantially antiparallel to the first desired spin axis. A tumbling motion is induced in the satellite so that a spin axis of the satellite oscillates between the first desired spin axis and the second desired spin axis. The tumbling motion is induced by sensing at least one component of the angular rate vector and controlling a single degree of freedom momentum storage device based upon the at least one component of the angular rate vector. The single degree of freedom momentum storage device has an orientation of variation substantially perpendicular to the desired spin axis. The single degree of freedom momentum storage device is controlled so that the first desired spin axis is made an intermediate inertia axis of an effective inertia matrix. A capture point is detected at which the angular rate vector is sufficiently close to the second desired spin axis to be recaptured. After detecting the capture point, the single degree of freedom momentum storage device is controlled so that the angular rate vector substantially aligns with the second desired spin axis.

摘要翻译： 公开了一种方法和系统，用于颠倒围绕第一期望自旋轴的卫星旋转，以围绕基本上反平行于第一所需旋转轴的第二期望自旋轴旋转。 在卫星中引起滚动运动，使得卫星的旋转轴在第一期望旋转轴和第二所需旋转轴之间振荡。 通过感测角速率矢量的至少一个分量并且基于角速率矢量的至少一个分量来控制单个自由度动量存储装置来感应翻滚运动。 单自由度动量存储装置具有基本上垂直于期望旋转轴的变化方向。 控制单自由度动量存储装置，使得第一期望旋转轴成为有效惯性矩阵的中间惯性轴。 检测捕获点，其中角速度矢量足够接近第二期望的旋转轴以被重新捕获。 在检测到捕获点之后，控制单个自由度动量存储装置，使得角速度矢量基本上与第二期望的旋转轴对齐。

公开(公告)号：US5667171A

公开(公告)日：1997-09-16

申请号：US430636

申请日：1995-04-28

申请人： Richard A. Fowell ,  John F. Yocum

发明人： Richard A. Fowell ,  John F. Yocum

IPC分类号： B64G1/24 ,  B64G1/28 ,  B64G1/36 ,  B64G1/38 ,  G05D1/08

CPC分类号： B64G1/24 ,  B64G1/281 ,  B64G1/285 ,  B64G1/288 ,  B64G1/36 ,  B64G1/38 ,  G05D1/0883 ,  B64G1/283 ,  B64G1/286 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365

摘要： Methods and systems for stabilizing satellite spin about an intermediate inertia axis (Z) are disclosed. A set of gyros (22) sense the X component and the Y component of the angular velocity of the satellite body. A single degree of freedom momentum wheel (26) has a fixed transverse orientation with respect to the intermediate axis in order to store momentum. In one embodiment, the momentum wheel (26) is oriented to store momentum parallel to the Y axis. A tachometer (30) senses the rotation rate of the momentum wheel (26). A processor (24) forms a control signal representative of a control torque to be applied to the momentum wheel (26). The control torque is based upon the X component and the Y component of angular velocity of the satellite, and the angular velocity of the momentum wheel (26). These methods and systems may also be used to invert the spin direction of spinning satellites, ensure tumble recover to a preferred orientation, and stabilize the body spin axis against nutation, dynamic imbalance and external torques.

摘要翻译： 公开了围绕中间惯性轴（Z）稳定卫星旋转的方法和系统。 一组陀螺仪（22）感测卫星体的角速度的X分量和Y分量。 单个自由度动量轮（26）相对于中间轴线具有固定的横向取向以便储存动量。 在一个实施例中，动量轮（26）被定向成存储平行于Y轴的动量。 转速计（30）感测动量轮（26）的旋转速度。 处理器（24）形成表示要施加到动量轮（26）的控制扭矩的控制信号。 控制扭矩基于卫星的角速度的X分量和Y分量以及动量轮（26）的角速度。 这些方法和系统也可以用于反转旋转卫星的旋转方向，确保滚筒恢复到优选的方向，并且使身体旋转轴线抵抗章动，动态不平衡和外部扭矩。